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74-24-07: 74-24-07 CHROMALLOY: Amendment 39-2021 as amended by Amendment 39-2080. Applies to Chromalloy Model RLB-6 Series rescue locator beacons incorporating battery packs, P/N A3-01-0175, installed in emergency equipment (including, but not limited to, slide-raft combinations and life rafts). Compliance required as indicated unless already accomplished: (a) On or before December 2, 1974, remove from service all Chromalloy Model RLB-6 Series rescue locator beacons or the battery packs incorporated in those units. (b) Contrary provisions of Sections 121.339, 121.353, and 135.163 of the Federal Aviation Regulations notwithstanding, Part 121 and 135 operators of aircraft, equipped with life rafts or slide-raft combinations incorporating Chromalloy Model RLB-6 Series rescue locator beacons may, after removal of such beacons or their battery packs pursuant to paragraph (A), continue to operate the aircraft (1) After replacing the battery packs with Chromalloy battery packs,P/N P4-01-0044, marked "FAA approved for use only as a replacement battery under AD 74-24-07."; (2) After replacing the affected beacons with FAA approved replacement beacons; or (3) Pending compliance with subparagraphs (1) or (2) of this paragraph, after installing in the aircraft an FAA approved portable type emergency locator transmitter that is accessible to the flight crew. (Note: Chromalloy Model RLB-6 Series rescue locator beacons that incorporate battery packs, P/N P4-01-0044, meet the performance requirements of TSO-C91 except their "low operating temperature" is +29 degrees F). Amendment 39-2021 was effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram, dated November 9, 1974, which contained this amendment. This amendment 39-2080 is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the telegram, dated November 15, 1974, which contained this amendment.
2012-09-03: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports of hydraulic accumulator failure. This AD requires replacing certain hydraulic accumulators with stainless steel hydraulic accumulators, and structural modifications in the nose landing gear bay. We are issuing this AD to prevent failure of hydraulic accumulators, which may result in damage to the airplane and injury to occupants.
74-02-01: 74-02-01 BELL: Amdt. 39-1769. Applies to Model 205A-1 and 212 helicopters, certificated in all categories, equipped with tail rotor hub assembly, P/N 212-010-701. Compliance required within the next 25 hours' time in service after the effective date of this A.D., unless already accomplished within the last 25 hours' time in service, and thereafter at intervals not to exceed 25 hours' time in service from the last inspection. To detect possible cracks or excessive looseness in the tail rotor trunnion bearings, accomplish the following: (a) Using a 3 power magnifying glass, inspect the trunnion bearing (P/N 212-010- 723-1 or P/N 212-010-768-1) exposed outer races for cracking. (b) To detect any axial looseness in the trunnion bearings, grasp the hub assembly and attempt to move it towards and away from the tail boom fin assembly. If trunnion bearing movement is considered excessive, remove the tail rotor hub and blade assembly. Measure the amount of axial playin each trunnion bearing using a dial indicator. (c) If there is evidence of either trunnion bearing outer race cracking or axial play in excess of the maximum allowable .015 inch, replace the affected bearing in accordance with the instructions contained in Bell Model 212 Overhaul Manual, dated May 1, 1972, Chapter-Section 65-20-01. (Bell Helicopter Company Service Bulletin Nos. 205-05-73-5, dated August 23, 1973, and 212-05-73-4, dated August 20, 1973, pertain to this subject.) The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Bell Helicopter Company, P. O. Box 482, Fort Worth, Texas 76101. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA,4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this A.D. which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas. This amendment becomes effective February 22, 1974.
66-22-06: 66-22-06 VICKERS: Amdt. 39-282 Part 39 Federal Register September 7, 1966. Applies to Viscount Models 744 and 745D Series Airplanes. Within the next 1,000 hours' time in service after the effective date of this AD, unless already accomplished, install replacement access panels and cowls for the inverters in accordance with British Aircraft Corporation Ltd. Modification Bulletin No. D.3157 or later ARB-approved issue or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, Middle East Region. This directive effective October 7, 1966.
74-18-12: 74-18-12 AIRESEARCH MANUFACTURING COMPANY of ARIZONA: Amendment 39-1941. Applies to AiResearch Model TFE 731-2-2B engines installed in, but not limited to Lear-Gates Learjet model 35/36 Aircraft, certificated in all categories. (A) Before further flight, unless previously accomplished, and prior to the installation of replacement fuel control assemblies, replace the hydromechanical fuel control orifice assembly in accordance with AiResearch Alert Service Bulletin TFE 731-A73-3006, dated August 12, 1974, or later FAA approved revisions. (B) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. (C) Aircraft may be flown to a base for performance of maintenance required by this AD per FAR's 21.197 and 21.199. This amendment is effective September 3, 1974, for all persons except those to whom it was made effective immediately by telegram dated August 5, 1974.
2012-08-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by test reports that showed that failure of a retract port flexible hose of a main landing gear (MLG) retraction actuator could cause excessive hydraulic fluid leakage. This AD requires a detailed inspection for defects and damage of the retract port flexible hose on the left and right MLG retraction actuator and replacement of the flexible hose if needed. We are issuing this AD to detect and correct defects and damage of the retract port flexible hose which could lead to an undamped extension of the MLG and could result in MLG structural failure, leading to an unsafe asymmetric landing configuration.
50-41-01: 50-41-01 TAYLORCRAFT: Applies to All Model B Series Aircraft, Serial Numbers 1001 and Up. Compliance required not later than November 15, 1950. Reports have been received of interference between the elevator horn bolt and the fin cover plate apparently caused by improper field installation of the cover plate through bolt. Cases are known where the bolt has worn through the cover plate and such interference may result in jamming of the elevator control system. An inspection of the parts should be made and if evidence of interference is noted, suitable means of preventing the cover plates from interfering with the elevator horn bolt should be incorporated; a spacer bushing at least 1/4 x 0.028 x 1 1/4 inches installed around the cover plate through bolt is considered satisfactory. (Taylorcraft, Inc. Service Bulletin 65 covers this same subject.)
68-11-01: 68-11-01\tBOEING: Amendment 39-605. Applies to Model 707 Series airplanes equipped with Collins Model 51RV-1 navigation receivers and Pratt & Whitney P/N 563586 or General Laboratories P/N 42721 solid state engine ignitor systems. \n\tCompliance required as indicated. \n\tReports indicate a localizer course indicator error may exist when the Pratt & Whitney P/N 563586 or General Laboratories P/N 42721 solid state engine ignitors are turned "ON". Since this unsafe condition is likely to exist in other Boeing Model 707 Series airplanes, the Director determined that: \n\tA.\tFlight operations shall not be predicated on the use of localizer receiver information when engine ignition systems are "ON". \n\tB.\tThe operating limitations specified in subparagraph A of this paragraph must be placed in the aircraft in the form of a placard in clear view of the pilot. For purposes of this AD any documents including a pilot check list including these limitations constitute a placard within the meaningof this paragraph. \n\tC.\tThis limitation does not apply when a 1000 microfarad 50 volt capacitor has been installed across the 28 volt DC input lead to the Collins 51RV-1 receiver in the radio junction box in accordance with Boeing telegraphic Alert Bulletin 2752 dated May 10, 1968, or an equivalent suppression system approved by the Western Region Aircraft Engineering Division. \n\tThis amendment becomes effective on May 31, 1968, for all persons except those to whom it was made effective immediately by telegram dated May 10, 1968.
2012-08-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of two failures of the single-tabbed bracket on the rudder. This AD requires replacing certain single-tabbed bonding brackets in the airplane empennage with two-tabbed bonding brackets. This AD also requires, for certain airplanes, installing new bonding jumpers, and measuring the resistance of the modified installation to verify resistance is within specified limits. We are issuing this AD to prevent failure of the bonding jumper bracket, which could result in loss of lightning protection ground path, which could \n\n((Page 24358)) \n\nlead to increased lightning-induced currents and subsequent damage to composite structures, hydraulic tubes, and actuator control electronics. In the event of a lightning strike, loss of lightning ground protection could result in the loss of control of the airplane.
71-19-02: 71-19-02 SOCIETE NATIONAL INDUSTRIELLE AEROSPATIALE (S.N.I.A.S.): Amendment 39-1281. Applies to Sud Model SE.210, MK. V1-R "Caravelle" airplanes. To prevent a possible fire due to unnoticed overheating of a hydraulic system, within the next 500 hours' time in service after the effective date of this AD, unless already accomplished, incorporate S.A. Modification 1262 by installing a Green and Blue Hydraulic System Fluid Overheat Detection System in accordance with Sud Service-Caravelle Bulletin No. 29-70, Revision 10, dated October 12, 1970, or later SGAC-approved issue or an FAA-approved equivalent. This amendment becomes effective September 27, 1971.